EP1764481A2 - Stator vane with ceramic airfoil and metallic platforms - Google Patents
Stator vane with ceramic airfoil and metallic platforms Download PDFInfo
- Publication number
- EP1764481A2 EP1764481A2 EP06254486A EP06254486A EP1764481A2 EP 1764481 A2 EP1764481 A2 EP 1764481A2 EP 06254486 A EP06254486 A EP 06254486A EP 06254486 A EP06254486 A EP 06254486A EP 1764481 A2 EP1764481 A2 EP 1764481A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- airfoil
- stator vane
- interface
- platforms
- vane assembly
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
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Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/284—Selection of ceramic materials
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
- F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
- F05D2300/6033—Ceramic matrix composites [CMC]
Abstract
Description
- This invention relates generally to turbine nozzle assemblies and specifically, to platform interface configurations for stage 2 CMC nozzle vanes.
- Sealing between high temperature components such as ceramic matrix composite (CMC) nozzle vanes and radially inner and outer metallic attachments or platforms problems relating to steep thermal gradients with associated high thermal stresses and reduced component life; internal pressure due to cooling air resulting in air flow wall distortion; and time varying performance erosion due to historical seal degradation. Eliminating the seal between a CMC vane and metal inner and outer platforms, however, results in an open channel for hot gas ingestion. Accordingly, there remains a need for a new geometry at the interface of the CMC vane and either one or both of the radially inner and outer metallic platforms that accommodates the inherent difficulties in the matching of ceramic and metal components, and that also eliminates the need for separate and discrete sealing elements. Seai-less design is also synonymous with unpressurized vane design.
- Controlled leakage is the key to the success of a seal-less design. Controlled leakage can be accommodated by creative interface configurations on the platform interface surface, the vane interface surface, or both. In the exemplary embodiments of this invention, creative interface configurations are provided that establish a circuitous gas leak path for increased flow resistance, resulting in the desired controlled leakage.
- In the various embodiments described herein, a CMC stator vane (also referred to herein as an airfoil shell or, simply airfoil) is assembled between a pair of radially inner and outer metal platforms that may be radially interconnected by a pair of spars extending through the airfoil shell. Each of the platforms is formed on its interior face with an airfoil-shaped recess adapted to receive the CMC airfoil shell. The seal-less configurations described herein are located on the airfoil shell and/or on adjacent interior peripheral surfaces of the airfoil-shaped recesses on the inner and/or outer platforms.
- In one exemplary embodiment, mating step joints are formed on the peripheral surface of each platform recess and the respective adjacent airfoil shell surfaces.
- In a second exemplary embodiment, the interface configuration is in the form of a scarf joint, i.e., with mating angled surfaces extending about the adjacent peripheries of each platform recess and respective airfoil shell surface.
- In a third exemplary embodiment, the platform airfoil surfaces are formed with a plurality of laterally projecting, abradable knife edges that interface with adjacent smooth surfaces on the airfoil shell.
- In a fourth exemplary embodiment, a compliant or spring interface is provided on the peripheral surface of each platform recess for engagement with a respective smooth surface on the adjacent airfoil shell. It will be appreciated that the free end or edge surface of the compliant interface may also be formed with a step joint or scarf joint as described above, to interface with the adjacent mating surface on the respective airfoil shell to provide the desired circuitous or tortuous path.
- Accordingly, in one aspect, the present invention relates to a stator vane assembly for a gas turbine comprising a ceramic matrix composite airfoil held between radially inner and outer metal platforms wherein an interface between the airfoil and at least one of the radially inner and outer platforms is shaped to create a circuitous leakage path for gas from the gas turbine hot gas path.
- In another aspect, the invention relates to a stator vane assembly for a gas turbine comprising a ceramic matrix composite airfoil held between radially inner and outer metal platforms wherein each of the platforms is formed with a recess adapted to receive the inner and outer platforms, each recess including a peripheral edge, the peripheral edge shaped to create the circuitous leakage path in cooperation with an adjacent surface on the airfoil.
- In still another aspect, the invention relates to a stator vane assembly for a gas turbine comprising a ceramic matrix composite vane held between radially inner and outer metal platforms wherein an interface between the vane and at least one of the radially inner and outer platforms is shaped to provide a compliant face for engagement with a smooth surface on the vane.
- The invention will now be described in greater detail, by way of example, with reference to the drawings, in which:-
- FIGURE 1 is a perspective exploded view of a CMC airfoil shell and associated inner and outer metal platforms connected by radial spars;
- FIGURE 2 is a schematic of a baseline or reference configuration at the interface of a CMC airfoil shell and a radially inner metal platform;
- FIGURE 3 is a schematic of a step joint interface between a CMC airfoil shell and an inner metal platform in accordance with a first exemplary embodiment of the invention;
- FIGURE 4 is a schematic of a scarf joint interface between a CMC airfoil shell and an inner metal platform in accordance with a second exemplary embodiment of the invention;
- FIGURE 5 is a schematic of an abradable knife edge interface between a CMC airfoil shell and an inner metal platform in accordance with a third exemplary embodiment of the invention;
- FIGURE 6 is a schematic illustrating a compliant interface between a CMC airfoil shell and an inner metal platform in accordance with a fourth exemplary embodiment of the invention;
- FIGURE 7 is a schematic of a combined compliant/step joint interface between a CMC airfoil shell and an inner metal platform in accordance with a fourth exemplary embodiment of the invention; and
- FIGURE 8 is a schematic of a combined compliant scarf joint interface between a CMC airfoil shell and an inner metal platform in accordance with a fifth exemplary embodiment of the invention.
- With reference to Figure 1, a CMC airfoil shell and
metal platform assembly 10 is shown in exploded form. More specifically, a pair of radially inner andouter metal platforms radial spars shaped recesses metal platform surfaces larger spar 18 is in the shape of a hollow channel that supplies cooling air to theairfoil shell 28. In this regard, theairfoil shell 28 is a hollow member that can be slidably received over the spars during assembly, with opposite ends of the airfoil shell received in therecesses platforms - In an alternative arrangement, the
spars external airfoil shell 28 in telescoping relationship, with appropriate dimensional tolerances. - As illustrated in Figure 1, the
recesses airfoil shell 28. It will be appreciated that the tolerances between the airfoil shell and the platform recesses must be controlled to avoid harmful excessive vibration, but at the same time, avoid problems associated with thermal mismatch between the components. - Turning to Figure 2, the
airfoil shell 28 is schematically represented as seated in the airfoil-shaped recess 20 of theinner metal platform 24. Therecess 20 is defined by the closedperipheral edge 30 that interfaces withsurfaces airfoil shell 28. This illustration provides a baseline reference for the interface configurations described below. In this regard, the unique interface configurations described herein are formed at the interface betweenrecess surface 30 and opposedsurfaces inner platform 24, and/or at the radiallyouter platform 14. For convenience, only the interfaces at the radially inner platforms are shown. - With reference now to Figure 3, the
CMC airfoil shell 36 is shown in assembled relationship with aninner metal platform 38. In this example, the interface configuration (or simply interface) is in the form of a step joint, with laterallyoriented steps peripheral edge 43 of the lower platform recess 44 engaged withlateral shoulders airfoil shell 36. Note that this arrangement allows the insertion of the airfoil shell from below thelower platform 38. The step joint at the opposite end of the airfoil shell would be reversed, however, to permit one-way installation of theshell 36 between both the inner and outer platforms. With appropriate tolerances between the interfacing surfaces, it will be appreciated that any gas leaking out of the hot gas path of the turbine, will necessarily be forced to follow a circuitous route through the interface, establishing the desirable controlled leakage, and without having to use discrete sealing elements. - With reference now to Figure 4, another interface is illustrated that is of simpler design than the configuration in Figure 3. Specifically, a
CMC airfoil shell 50 is shown in assembled relationship with respect to aninner metal platform 52. In this embodiment, the radiallyinner platform recess 54 is formed with aperipheral edge surface 56 that is slanted at about a 45° angle to a radial centerline through theairfoil shell 50. At the same time, thelower surface 58 of theairfoil shell 50 is formed at a similar angle, thus forming a scarf joint between the airfoil shell and theinner platform 52. Here again, for purposes of facilitating one-way installation, the interface at the upper end of the airfoil shell would be reversed. - In Figure 5, yet another embodiment is shown where a
CMC airfoil shell 58 is seated within therecess 62 in theinner metal platform 60. In this embodiment, therecess 62 in theplatform 60 is formed with aperipheral edge 63 made up of a plurality of inwardly projecting abradable knife edges 64 (four shown), spaced from each other in the radial direction. Theedges 64 interface with an adjacentsmooth surface 66 on theairfoil shell 58, with appropriate tolerance between the two. Here again, it will be appreciated that resistance to leakage gas is increased by reason of the circuitous path through the platform. - In Figure 6, a compliant interface is provided between a
CMC airfoil shell 68 and aninner metal platform 70. In this embodiment, therecess 72 in the inner platform is formed with a peripheral edge having oppositely directed cutouts orslots edge 80 of therecess 72 to act in the nature of a spring, in compliant or resilient "engagement" (i.e., with minimal clearance) with an adjacentsmooth surface 78 of the airfoil shell. In order to incorporate the circuitous leakage gas feature of the earlier-described embodiments, it will be appreciated that theedge 80 of theplatform recess 72 may be configured to incorporate a step joint as illustrated in Figure 3 or a scarf joint as illustrated in Figure 4. These alternative interface configurations are shown schematically in Figures 7 and 8, respectively. Specifically, Figure 7 shows a compliant step joint where theCMC airfoil shell 82 is seated within therecess 84 in aninner metal platform 86, with theedge 88 of the compliant recess (formed by slots 90) formed with astep joint 92 that interfaces with acomplementary step joint 94 on the airfoil shell. - In Figure 8, the
CMC airfoil shell 96 is seated within therecess 98 in aninner metal platform 100, with theedge 102 of the recess 84 (formed by slots 104) formed with anangled surface 106 that interfaces with a complementary angledperipheral surface 108 on theairfoil shell 96, thus forming a compliant scarf joint at the interface. - By providing increased flow resistance resulting in controlled leakage, it is possible to eliminate the steep thermal gradients and associated reduction in thermal stresses and increased component life; thinner wall sections of the CMC vane to the elimination of internal pressure due to cooling air; and robust consistent performance by eliminating seal degradation.
Claims (10)
- A stator vane assembly for a gas turbine comprising a ceramic matrix composite airfoil (36) held between radially inner and outer metal platforms (38, 14) wherein an interface between said airfoil and at least one of said radially inner and outer platforms is shaped to create a circuitous leakage path for gas from the gas turbine.
- The stator vane assembly of claim 1 wherein said interface comprises mating stepped surfaces (40, 42).
- The stator vane assembly of claim 1 wherein said interface comprises a mating scarf joint (56, 58).
- The stator vane assembly of claim 1 wherein said interface comprises plural abradable knife edges (64) on said radially inner platform adjacent a smooth surface (66) on said airfoil.
- The stator vane assembly of any one of claims 1 to 4 wherein said interface is located at said radially inner platform (38).
- The stator assembly of claim 5 wherein a second substantially identical interface is located at said radially outer platform (14).
- The stator vane assembly of claim 2 wherein said mating stepped surfaces (40, 42) include at least two steps perpendicular to a radial centerline through said vane.
- The stator vane assembly of claim 3 wherein said scarf joint includes mating surfaces (56, 58) at an angle of about 45° relative to a radial centerline through said vane.
- The stator vane assembly of claim 4 wherein said plural abradable knife edges (64) comprise at least four projections terminating in radial surfaces adjacent said smooth surface (66) on said airfoil.
- A stator vane assembly for a gas turbine comprising a ceramic matrix composite airfoil (16) held between radially inner and outer metal platforms (38, 14) wherein each of said platforms is formed with a recess adapted to receive said inner and outer platforms, each recess including a peripheral edge, said peripheral edge shaped to create said circuitous leakage path in cooperation with an adjacent surface on said airfoil.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/228,251 US7329087B2 (en) | 2005-09-19 | 2005-09-19 | Seal-less CMC vane to platform interfaces |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1764481A2 true EP1764481A2 (en) | 2007-03-21 |
EP1764481A3 EP1764481A3 (en) | 2008-12-17 |
Family
ID=37216171
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06254486A Withdrawn EP1764481A3 (en) | 2005-09-19 | 2006-08-29 | Stator vane with ceramic airfoil and metallic platforms |
Country Status (5)
Country | Link |
---|---|
US (1) | US7329087B2 (en) |
EP (1) | EP1764481A3 (en) |
JP (1) | JP2007085342A (en) |
KR (1) | KR20070032612A (en) |
CN (1) | CN1936277A (en) |
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Also Published As
Publication number | Publication date |
---|---|
KR20070032612A (en) | 2007-03-22 |
US7329087B2 (en) | 2008-02-12 |
JP2007085342A (en) | 2007-04-05 |
EP1764481A3 (en) | 2008-12-17 |
CN1936277A (en) | 2007-03-28 |
US20070065285A1 (en) | 2007-03-22 |
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